An implicit LES code utilizing the Weighted Compact Nonlinear Scheme is developed. A shock diffraction problem and the boundary layer flow over a flat plate are solved to examine the applicability of the developed code for compressible turbulent flowfleld. A supersonic flowfleld over a backward-facing step both in two- and three-dimensional space is then solved. It is shown that characteristic features of the flowfleld are well captured in the computed results. However, a quantitative agreement of the surface pressure profile along the centerline with that of the experimental data is yet to be accomplished. Possible causes are examined.
|Journal||Collection of Technical Papers - AIAA Applied Aerodynamics Conference|
|Publication status||Published - 2008 Jan 1|
|Event||26th AIAA Applied Aerodynamics Conference - Honolulu, HI, United States|
Duration: 2008 Aug 18 → 2008 Aug 21
ASJC Scopus subject areas